EP0664852B1 - Mechanische verriegelung für die schubumkehrvorrichtung eines strahltriebwerkes - Google Patents

Mechanische verriegelung für die schubumkehrvorrichtung eines strahltriebwerkes Download PDF

Info

Publication number
EP0664852B1
EP0664852B1 EP93921845A EP93921845A EP0664852B1 EP 0664852 B1 EP0664852 B1 EP 0664852B1 EP 93921845 A EP93921845 A EP 93921845A EP 93921845 A EP93921845 A EP 93921845A EP 0664852 B1 EP0664852 B1 EP 0664852B1
Authority
EP
European Patent Office
Prior art keywords
actuator
shaft
thrust reverser
movement
synchronizing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP93921845A
Other languages
English (en)
French (fr)
Other versions
EP0664852A1 (de
Inventor
Timothy O. Repp
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Publication of EP0664852A1 publication Critical patent/EP0664852A1/de
Application granted granted Critical
Publication of EP0664852B1 publication Critical patent/EP0664852B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54Nozzles having means for reversing jet thrust
    • F02K1/76Control or regulation of thrust reversers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54Nozzles having means for reversing jet thrust
    • F02K1/76Control or regulation of thrust reversers
    • F02K1/766Control or regulation of thrust reversers with blocking systems or locking devices; Arrangement of locking devices for thrust reversers
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/60Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention pertains to an airplane thrust reverser system comprising:
  • Such a thrust reverser system is known from US-A-4 391 409.
  • This known thrust reverser comprises two complementary cowls, each of which is moved between its stowed and deployed position by a set of three hydraulic actuators.
  • the actuators of each set are coupled both hydraulically by means of common hydraulic supply lines, and mechanically by means of a rotatable flexible synchronization shaft.
  • a jet engine thrust reverser operates to redirect either engine exhaust gases or engine fan air in a lateral and/or forward direction to aid in slowing an airplane during landing rollout.
  • thrust reverser operation is initiated by the pilot once the airplane has touched down on the runway during landing. Redirection of the airflow is accomplished by a series of rotating blocker doors which, upon placement of the cockpit thrust reverser levers in the proper position by the pilot, are pivoted from a stowed position into a location blocking either the exhaust gas stream or the fan bypass air. It is usually desirable that the thrust reverser blocker doors remain in the stowed position until commanded actuation in response to the movement of the thrust reverser levers.
  • the thrust reverser system disclosed in the above identified prior art document US-A-4 391 409 comprises two locking systems.
  • the first locking system is a so-called isolation valve assembly, which cuts of the entire hydraulic system of the thrust reverser from the main hydraulic system of the aircraft
  • the second locking system consists of two hydraulic valves, each of which shuts off the hydraulic fluid supply to one set of actuators, and further actuates a mechanical lock acting on one of these actuators.
  • the hydraulic valves of both locking systems are spring biased to a locked position, and are solenoid operated to move to a release position in which movement of the thrust reverser cowls is permitted.
  • a thrust reverser system which comprises mechanically actuated screwjacks for moving the thrust reverser cowl. These screwjacks are each driven via a bevel gear, which is connected to a single rotating drive shaft arranged in peripheral direction in the engine nacelle.
  • the drive shaft is provided with a one way locking device or ratchet, comprising substantially triangular pawls arranged radially on the drive shaft, and a locking bar, which is pivottaly mounted to a spring biased solenoid operated rod.
  • the solenoid When the solenoid is not energized, the bar is held against the rotary drive shaft and engages the flat face of one of the ratchet pawls, thus preventing rotation of the drive shaft and actuation of the screwjacks.
  • the present invention seeks to provide a thrust reverser system of the type described above, having improved locking means. According to the invention, this is accomplished in that said locking means are arranged for engaging the synchronizing means so as to prevent movement of the actuator gear and the piston.
  • the locking means act on the synchronizing shaft, instead of on one of the actuators, the locking loads acting on the locking means are much smaller, as the synchronizing means are laid out for rotation at relatively high speed and relatively low torque, contrary to the actuators, which are designed for low rotational speed and high torque.
  • FIG. 1 there is shown a conventional aircraft nacelle indicated at 18 which includes a jet engine, such as a Pratt & Whitney PW4000, indicated at 20 (shown in hidden lines) supported by a strut 22 on a wing 24 (only a portion of which is shown).
  • the nacelle 18 includes a nose cowl 26, a fan cowl 27, a thrust reverser sleeve 28, a core cowl 30 and nozzle exhaust 32.
  • the thrust reverser system includes an inner duct (fan duct cowl) 36 and outer sleeve 28.
  • the sleeve 28 translates in an aft direction indicated by an arrow identified by a number 42 in FIG. 2, and a forward direction indicated by an arrow identified by a number 44.
  • the thrust reverser When the thrust reverser is deployed, the translating sleeve 28 moves aft from a "stowed" position shown in FIG. 1 to a "deployed" position shown in FIG. 2.
  • cascade vanes 46 (FIG. 2) mounted to a thrust reverser support structure are uncovered. Vanes 46 are slanted in a forward direction so that during thrust reverser operation, fan air from the engine is re-directed forward through the vanes to aid in stopping the airplane.
  • Air driven aft by the engine fan flows along an annular duct 48 (FIG. 3) formed by the fan duct cowl 33 and the thrust reverser sleeve 28. Movement of the sleeve 28 in the aft direction, causes blocker doors 50 to pivot to from their stowed positions (shown in FIG. 3) to their deployed positions (not shown) where the doors are positioned to block rearward movement of the air through duct 48. In this manner all rearward movement of the engine fan air is redirected forward through the cascade vanes 46.
  • Movement of the sleeve 28 is guided along a pair of parallel tracks 51 (FIG. 3) mounted to the top and bottom of the fan duct cowl 36 in a fore and aft direction.
  • the sleeve 28 is moved between the stowed and deployed positions by means of a number of hydraulic actuators indicated at 54 (FIG. 3), each having an actuator rod 56 which is connected to the sleeve 28. More specifically, as shown in FIGS. 5 and 6, each actuator 54 is connected to a structural torque box 57 via a gimbal mount 61 thereby allowing the actuator to accomodate lateral variances in sleeve motion. As shown in FIG.
  • the actuator rod 56 is located inside the aerodynamic surface of sleeve 28 and is connected to the sleeve 28 by a ball joint 68.
  • the ball joint 68 is accessible by removing a panel 70 which is bolted to the exterior surface of the sleeve 28.
  • the actuator rod 56 In operation, when the thrust reverser is commanded by the pilot to the deployed position, the actuator rod 56 (FIG. 5) extends in the aft direction. Conversely, when the thrust reverser is commanded by the pilot to move to the stowed position, the actuator rod 56 retracts in the forward direction.
  • the actuator 54 is a thrust reverser actuator currently installed on Boeing 767 airplanes.
  • each actuator 54 includes a double acting piston 72 which is extended in the rightward direction (with reference to FIG. 7) by hydraulic pressure acting against a face 74 of the piston 72. Retraction of the piston 72 and the thrust reverser sleeve therewith is accomplished by relieving hydraulic pressure from the piston face 74, so that hydraulic pressure acting against an opposing face 76 of the piston causes it to move in the leftward direction.
  • the piston 72 is connected to the actuator rod 56 which in turn is connected to the thrust reverser sleeve 28 in the manner described previously.
  • each thrust reverser sleeve is driven by three of the actuators 54 (FIG. 3). It is important that each actuator 54 extend and retract the sleeve at the same rate to avoid causing the sleeve to bind along the tracks 51. To accomplish this, operation of each of the three actuators 54 is synchronized by means of an interconnecting synchronizing shaft 80.
  • the sync shaft 80 (FIGS. 5 and 6) is a tube having a stationary outer sleeve and an internal rotating flexible shaft 81 which synchronizes motion of the three actuators.
  • the outer sleeve of the sync shaft 80 is connected to the actuator 54 by a swivel coupling 82.
  • extension and retraction of the thrust reverser sleeve results in rotation of the Acme screw 86-and rotary gear 94 therewith.
  • This causes rotation of the worm gear 90 in a manner that a high torque and low rotational speed input from the Acme screw 86 is converted by the worm gear 90 to a low torque and high rotational speed output to the sync shaft.
  • one of the actuators 54 attempts to move the thrust reverser sleeve at a different rate than the other actuators, their rates are equalized via the common sync shaft and through the respective worm gears, spur gears and Acme screws of the actuators. This results in uniform translation of the thrust reverser sleeve.
  • a manual drive clutch mechanism 96 shown in FIG. 6 is attached to the left end of the actuator.
  • the manual drive clutch 96 includes a socket (not shown) for receiving a square drive tool (also not shown) in its left end 95.
  • the manual drive clutch 96 is connected by a female coupling 97 to a threaded male connector 98 at the left end of the actuator.
  • the drive clutch 96 includes a drive shaft 99 (FIG. 10) having a square-ended tip which extends in a rightward direction from the clutch and which fits inside an end slot 100 (FIG. 5) of the actuator worm gear 90.
  • the purpose of the mechanical lock 104 is to prevent uncommanded translation of the thrust reverser sleeve.
  • the mechanical lock 104 includes a cylindrical housing 106 (FIG. 10) having an internal cylindrical passageway 108. Axially aligned with the centerline of the passageway 108 is a cylindrical shaft 110 having an eight-pointed splined slot 112 at its left end for receiving therein the splined end tip 99 of the clutch mechanism 96 described previously. At the right end of the shaft 110 is a splined tip 113 which is inserted in the socket 100 (FIG. 5) of the actuator worm gear 90.
  • Mounted centrally on the center shaft 110 (FIGS. 9 and 10) is a lock wheel 114 having a cylindrical outer surface 116.
  • Movement of the locking pin 120 (FIG. 10) between the locked position and an unlocked position (where the pin 120 is above and clear of the teeth 118) is controlled by an electrically operated solenoid 124 through which the upper end of the locking pin 120 extends. Electrical control is initiated at the cockpit (not shown) via conventional airplane thrust reverser control circuits and is transmitted by electrical wires 125 to the solenoid 124. Control of the solenoid may be accomplished in a conventional manner and is not part of the present invention. It should be appreciated that other means for controlling movement of the locking pin 120, such as hydraulic or electrohydraulic means, may be utilized.
  • a spring 126 biases the locking pin 120 in the locked position when the solenoid is not energized.
  • the spring 126 is positioned between the bottom surface of the solenoid 124 and a shoulder 128 attached to the locking pin 120.
  • the solenoid 124 is located inside a columnar housing 129 extending upward from the lower housing 106.
  • the column 129 includes a ledge 130 which supports the shoulder 128 and the locking pin therewith when it is in the locking position.
  • the solenoid 124 When the thrust reverser is being deployed or stowed, the solenoid 124 is energized causing the locking pin 120 to move upward against the force of the spring 126 thereby allowing the locking wheel 114 and the shaft 110 to rotate freely.
  • electrical power to the solenoid is terminated and the spring 126 moves the locking pin 120 into the locking (down) position thereby preventing rotation of the locking wheel 114 and the shaft 110.
  • the locking loads generated by the locking wheel 114 are very small because of the low torque transferred from the the worm gear 90. This allows the mechanical lock 104 to be smaller and lighter in weight than locks attached directly to the thrust reverser sleeve.
  • the central shaft 110 is supported in the housing toward the left end of the housing by bearing 132 and toward the right end of the housing by bearing 134.
  • the right end of the housing 106 includes a collar 136 which is rotatable with respect to the housing.
  • the collar 136 is internally threaded to allow it to be screwed onto the threaded male fitting 98 (FIG. 6) extending from the left end of the thrust reverser actuator.
  • the left end of the housing 106 includes an externally threaded male fitting 138 which allows the swivel coupling 97 (FIG. 6) located at the right end of the manual clutch mechanism 96 to be screwed thereon.
  • sync lock mechanism incorporates the manual drive mechanism within housing 106.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmission Devices (AREA)

Claims (9)

  1. Flugzeug-Schubumkehrsystem, mit:
    a) Mitteln (28, 50) zum Umlenken von Luft, die in Rückwärtsrichtung von einem Flugzeugtriebwerk (20) angetrieben ist, in einer nicht nach hinten gerichteten Richtung;
    b) Betätigungsmitteln mit mindestens zwei Betätigungselementen (54), die mit getrennten Stellen der Luftumlenkmittel (28, 50) verbunden sind, um die Luftumlenkmittel (28, 50) zwischen einer Unterbringungslage, wo die Luft nicht umgelenkt ist, und einer Ausfahrlage zu bewegen, in der die Luft in der nicht nach hinten gerichteten Richtung umgelenkt ist; wobei jedes Betätigungselement (54) einen hydraulisch angetriebenen, doppelt wirkenden Kolben (72) aufweist, der mit den Luftumlenkmitteln (28, 50) verbunden ist;
    c) Mitteln (80) zum Synchronisieren des Betriebs der Betätigungselemente (54) auf eine solche Weise, daß die getrennten Stellen der Luftumlenkmittel (28, 50) zwischen der Unterbringungslage und der Ausfahrlage mit derselben Geschwindigkeit bewegt werden;
    d) einem Betätigungstrieb (84, 86, 94), der in jedem der Betätigungselemente (54) enthalten ist und in den Kolben (72) und die Synchronisiermittel (80) eingreift; und
    e) Sperrmitteln (104) zum Verhindern der Bewegung der Luftumlenkmittel (28, 50),
    dadurch gekennzeichnet, daß die genannten Sperrmittel (104) zum Eingriff in die Synchronisiermittel (80) so eingerichtet sind, daß die Bewegung des Betätigungstriebs (84, 86, 94) des Kolbens (72) verhindert ist.
  2. System, wie ausgeführt in Anspruch 1, dadurch gekennzeichnet, daß
    a) die Synchronisiermittel (80) einen Synchronisiertrieb (90) umfassen, der in den Betätigungstrieb (84, 86, 94) eingreift; und
    b) die Sperrmittel (104) folgende Merkmale aufweisen: (i) eine Welle (180), die in den Synchronisiertrieb (90) zur Bewegung hiermit eingreift, und (ii) Mittel (120, 124, 126, 128) zum Verhindern der Bewegung der Welle (110), wobei die Verhinderungsmittel (120, 124, 126, 128) zwischen einer ersten, unverriegelten Lage außer Eingriff mit der Welle (110) und einer zweiten, verriegelten Lage in Eingriff mit der Welle (110) auf eine solche Weise beweglich sind, daß deren Bewegung verhindert ist.
  3. System, wie ausgeführt in Anspruch 2, dadurch gekennzeichnet, daß
    a) die Welle (110) sich in einer Drehrichtung bewegt und eine Basis (116) umfaßt, die hiermit verbunden ist;
    b) die Verhinderungsmittel (120, 124, 126, 128) einen Anschlag (120, 128) aufweisen, der in der Sperrlage in die Basis (116) eingreift, um die Drehbewegung der Welle (110) zu verhindern.
  4. System, wie ausgeführt in Anspruch 3, dadurch gekennzeichnet, daß
    a) die Basis (116) mindestens eine Aufnahme aufweist; und
    b) der Anschlag (120, 128) eine Stange (120) umfaßt, die in der Sperrlage in die mindestens eine Aufnahme eingreift, um die Drehbewegung der Welle (110) zu verhindern.
  5. System, wie ausgeführt in Anspruch 4, dadurch gekennzeichnet, daß die mindestens eine Aufnahme durch mindestens zwei Zähne (118) gebildet ist, die von der genannten Basis (116) vorstehen.
  6. System, wie ausgeführt in Anspruch 4 oder 5, dadurch gekennzeichnet, daß
    a) die Verhinderungsmittel (120, 124, 116, 118) eine Feder (126) umfassen, die die Stange (120) in der Sperrlage in Eingriff mit der Aufnahme belastet; und
    b) die Verhinderungsmittel (120, 124, 126, 128) einen Elektromagneten (124) umfassen, der die Stange (120) in der unverriegelten Lage aus dem Eingriff mit der Aufnahme freisetzt.
  7. System, wie ausgeführt in Anspruch 6, dadurch gekennzeichnet, daß die Sperrmittel (104) ein Gehäuse (129) zum Lagern der Stange (120) auf eine solche Weise aufweisen, daß die Bewegung der Stange (120) längs ihrer Längsachse zum Herstellen und Lösen des Eingriffs mit der Aufnahme ermöglicht ist.
  8. System, wie ausgeführt in irgendeinem der vorangehenden Ansprüche, gekennzeichnet durch einen handbetriebenen Kupplungsmechanismus (96), der mit den genannten Synchronisiermitteln (80) verbunden ist.
  9. System, wie ausgeführt in Anspruch 8, dadurch gekennzeichnet, daß der handbetriebene Kupplungsmechanismus (96) mit der rotierenden Welle (110) der Sperrmittel (104) an deren Ende (112) verbunden sind, das dem Ende (113) entgegengesetzt ist, das in die genannten Synchronisiermittel (80) eingreift.
EP93921845A 1992-09-21 1993-09-21 Mechanische verriegelung für die schubumkehrvorrichtung eines strahltriebwerkes Expired - Lifetime EP0664852B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US94761892A 1992-09-21 1992-09-21
US947618 1992-09-21
PCT/EP1993/002585 WO1994007018A1 (en) 1992-09-21 1993-09-21 Mechanical lock for jet engine thrust reverser

Publications (2)

Publication Number Publication Date
EP0664852A1 EP0664852A1 (de) 1995-08-02
EP0664852B1 true EP0664852B1 (de) 1996-08-14

Family

ID=25486431

Family Applications (1)

Application Number Title Priority Date Filing Date
EP93921845A Expired - Lifetime EP0664852B1 (de) 1992-09-21 1993-09-21 Mechanische verriegelung für die schubumkehrvorrichtung eines strahltriebwerkes

Country Status (5)

Country Link
US (1) US5448884A (de)
EP (1) EP0664852B1 (de)
DE (1) DE69304080T2 (de)
RU (1) RU2120559C1 (de)
WO (1) WO1994007018A1 (de)

Families Citing this family (55)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5609020A (en) * 1995-05-15 1997-03-11 The Boeing Company Thrust reverser synchronization shaft lock
DE69514224T2 (de) * 1995-09-13 2000-08-10 Hurel Dubois Avions Elektrohydraulische Schubumkehrvorrichtung mit zwei Klappen
US5685141A (en) * 1995-12-26 1997-11-11 General Electric Company Lock for nozzle control in the event of hydraulic failure
CN1077217C (zh) * 1996-08-22 2002-01-02 波音公司 反推装置同步轴锁定机构
FR2755730B1 (fr) * 1996-11-14 1999-01-08 Hispano Suiza Sa Systeme de commande electrique pour inverseur de poussee de turboreacteur
GB9625001D0 (en) * 1996-11-30 1997-01-15 Lucas Ind Plc A lock for a thrust reverser mechanism and a thrust reverser mechanism
FR2762875B1 (fr) * 1997-04-30 1999-06-04 Hispano Suiza Sa Inverseur de poussee protege en cas de deverrouillage accidentel
FR2765916B1 (fr) * 1997-07-10 1999-08-20 Hispano Suiza Sa Inverseur de poussee a resistance amelioree aux impacts
FR2765917B1 (fr) * 1997-07-10 1999-08-20 Hispano Suiza Sa Inverseur de poussee a visualisation de verrouillage
US6021636A (en) * 1997-07-25 2000-02-08 Alliedsignal Inc. Lightweight tertiary thrust reverser lock assembly with a blocking member
GB9823697D0 (en) * 1998-10-30 1998-12-23 Lucas Ind Plc Deployment inhibiting arrangement for a thrust reverser system
US6519929B2 (en) 2001-04-30 2003-02-18 Honeywell International, Inc. System and method for controlling the deployment of jet engine thrust reversers
US6526744B2 (en) 2001-04-30 2003-03-04 Honeywell International Inc. System and method for controlling the stowage of jet engine thrust reversers
US6439504B1 (en) 2001-06-15 2002-08-27 Honeywell International, Inc. System and method for sustaining electric power during a momentary power interruption in an electric thrust reverser actuation system
US6681559B2 (en) 2001-07-24 2004-01-27 Honeywell International, Inc. Thrust reverser position determination system and method
US6584763B2 (en) 2001-08-01 2003-07-01 Rohr, Inc. Lock for the translating sleeve of a turbofan engine thrust reverser
US6625972B1 (en) * 2001-08-30 2003-09-30 The Boeing Company Thrust reverser sleeve lock
US6622474B1 (en) * 2001-08-31 2003-09-23 The Boeing Company Synchronization cross-feed system
US6487846B1 (en) 2001-09-07 2002-12-03 Honeywell International, Inc. Thrust reverser actuator including an integrated locking mechanism
US6786039B2 (en) * 2001-09-07 2004-09-07 Honeywell International, Inc. Thrust reverser actuator with an automatic relock and lock drop prevention mechanism
FR2830051B1 (fr) * 2001-09-27 2003-11-07 Hurel Hispano Le Havre Systeme de verrouillage sur un inverseur de poussee a grilles
US6684623B2 (en) 2002-02-27 2004-02-03 Honeywell International, Inc. Gearless electric thrust reverser actuators and actuation system incorporating same
US6622963B1 (en) 2002-04-16 2003-09-23 Honeywell International Inc. System and method for controlling the movement of an aircraft engine cowl door
FR2846376B1 (fr) * 2002-10-25 2005-01-28 Hispano Suiza Sa Platine de maintenance et d'inhibition pour inverseur de poussee
FR2846377B1 (fr) * 2002-10-25 2006-06-30 Hispano Suiza Sa Inverseur de poussee electromecanique pour turboreacteur a controle permanent de position
US6786315B1 (en) * 2003-03-28 2004-09-07 Honeywell International, Inc. Thrust reverser system with sequential torque decoupler
US7216581B2 (en) * 2004-01-16 2007-05-15 The Boeing Company Piston locking actuator
US7946105B2 (en) 2006-11-02 2011-05-24 Honeywell International Inc. Bi-directional locking ring assembly for aircraft thrust reverser manual drive unit
FR2920131B1 (fr) * 2007-08-20 2010-01-08 Aircelle Sa Nacelle de turboreacteur equipee d'un systeme d'inhibition mecanique d'un inverseur de poussee
US8201390B2 (en) * 2007-12-12 2012-06-19 Spirit Aerosystems, Inc. Partial cascade thrust reverser
US9188025B2 (en) * 2008-11-26 2015-11-17 Mra Systems, Inc. Apparatus for facilitating access to a nacelle interior
US8127532B2 (en) 2008-11-26 2012-03-06 The Boeing Company Pivoting fan nozzle nacelle
US9188026B2 (en) * 2008-11-26 2015-11-17 Mra Systems, Inc. Apparatus for facilitating access to a nacelle interior and method of assembling the same
US8959889B2 (en) 2008-11-26 2015-02-24 The Boeing Company Method of varying a fan duct nozzle throat area of a gas turbine engine
US8220738B2 (en) * 2008-11-26 2012-07-17 Mra Systems, Inc. Nacelle and method of assembling the same
US8960031B2 (en) * 2009-09-01 2015-02-24 Parker-Hannifin Corporation Aircraft stabilizer actuator
US8615982B2 (en) * 2011-07-05 2013-12-31 Hamilton Sundstrand Corporation Integrated electric variable area fan nozzle thrust reversal actuation system
US9086035B2 (en) * 2012-01-20 2015-07-21 Hamilton Sundstrand Corporation Integrated thrust reverser actuator and variable area fan nozzle actuator
US9188081B2 (en) * 2012-04-10 2015-11-17 Honeywell International Inc. Thrust reverser actuator with primary lock
FR2989739B1 (fr) 2012-04-23 2016-01-08 Sagem Defense Securite Dispositif d'actionnement pour deplacer un inverseur de poussee
FR2996602B1 (fr) 2012-10-08 2018-04-06 Sagem Defense Securite Dispositif d'actionnement incluant un dispositif de verrouillage primaire
US9309835B2 (en) 2012-11-16 2016-04-12 Woodward Hrt, Inc. Engine and thrust reverser actuation system
US9512910B2 (en) 2013-02-19 2016-12-06 Honeywell International Inc. Actuator including handling-proof position feedback mechanism
US9109536B2 (en) 2013-03-14 2015-08-18 Woodward Hrt, Inc. Engine thrust reverser lock
FR3010456B1 (fr) * 2013-09-09 2015-09-11 Sagem Defense Securite Dispositif d'entrainement d'actionneurs pour inverseur de poussee comprenant une unite d'entrainement manuel debrayable
FR3010455B1 (fr) * 2013-09-09 2015-09-11 Sagem Defense Securite Dispositif d'entrainement d'actionneurs pour inverseur de poussee permettant selectivement un entrainement motorise ou manuel
WO2015065428A1 (en) * 2013-10-31 2015-05-07 Triumph Actuation Systems -Yakima, Llc Thrust reverser system and engine assembly with lockout mechanism
FR3016928B1 (fr) * 2014-01-27 2019-04-19 Safran Nacelles Commande hydraulique d’inverseur de poussee de turboreacteur, comportant une machine a cylindree variable
FR3029171B1 (fr) * 2014-11-27 2016-12-30 Airbus Operations Sas Turbomachine d'aeronef presentant une entree d'air a section variable
US10543927B2 (en) * 2016-11-18 2020-01-28 Rohr, Inc. Lockable track system for a translating nacelle structure
FR3063527B1 (fr) * 2017-03-06 2019-04-05 Safran Electronics & Defense Verin a verrouillage integre
EP3462014B1 (de) * 2017-09-28 2021-06-09 Goodrich Actuation Systems Limited Elektrisch betätigter schubumkehrer mit verbessertem verriegelungssystem und drehmomentbegrenzer
CN110450973B (zh) * 2019-07-30 2022-11-22 中国航发沈阳发动机研究所 一种可调长度的反推对中支撑装置
US11434848B2 (en) 2019-11-05 2022-09-06 Rohr, Inc. Drive system for translating structure
US11326554B2 (en) * 2020-07-02 2022-05-10 Woodward, Inc. Hydraulic baulking sync lock

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3621763A (en) * 1969-07-17 1971-11-23 Pneumo Dynamics Corp Fan thrust reverser actuator
US4383647A (en) * 1980-08-22 1983-05-17 The Bendix Corporation Integrated hydraulic control circuit for jet engine thrust reverser and variable exhaust nozzle
US4391409A (en) * 1980-09-30 1983-07-05 The Boeing Company Positioning and control system for fan thrust reverser cowls in a turbofan engine
DE3222674C2 (de) * 1982-06-16 1984-04-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zum Verstellen von Schubumkehrern
GB2154291B (en) * 1984-02-14 1987-08-12 Rolls Royce Anti rotation device
EP0536954B1 (de) * 1991-10-10 1996-01-24 Lucas Industries Public Limited Company Verriegelung einer Schubumkehrvorrichtung

Also Published As

Publication number Publication date
US5448884A (en) 1995-09-12
DE69304080D1 (de) 1996-09-19
DE69304080T2 (de) 1996-12-19
WO1994007018A1 (en) 1994-03-31
EP0664852A1 (de) 1995-08-02
RU2120559C1 (ru) 1998-10-20

Similar Documents

Publication Publication Date Title
EP0664852B1 (de) Mechanische verriegelung für die schubumkehrvorrichtung eines strahltriebwerkes
US5609020A (en) Thrust reverser synchronization shaft lock
EP1554484B1 (de) Schubumkehrstellantrieb mit automatischem entriegelungsschutzmechanismus
US6935097B2 (en) Lock assembly that inhibits thrust reverser movement at or near the stowed position
US10330046B2 (en) Thrust reverser actuator with primary lock
US4391409A (en) Positioning and control system for fan thrust reverser cowls in a turbofan engine
US6625972B1 (en) Thrust reverser sleeve lock
US6598386B2 (en) Jet engine thrust reverser system having torque limited synchronization
US9709003B2 (en) Actuator device for moving a movable cowl of a thrust reverser
US9476384B2 (en) Actuation device for moving a movable cowling of a thrust-reverser
US6554224B2 (en) Out-of-plane thrust reverser sleeve lock
JP3874424B2 (ja) 油圧故障の場合のノズル制御のロック
US6604355B1 (en) Thrust reverser hook latch system
EP1288478B1 (de) System zur Synchronizierung einer Schubumkehr-Vorrichtung eines Flugzeuges
US20050001095A1 (en) Self-aligning thrust reverser system lock assembly
RU2152528C1 (ru) Система запирания вала синхронизации устройства реверсирования тяги и замок вала синхронизации устройства реверсирования тяги

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19950329

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB NL

17Q First examination report despatched

Effective date: 19950928

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB NL

REF Corresponds to:

Ref document number: 69304080

Country of ref document: DE

Date of ref document: 19960919

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed
REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: NL

Payment date: 20060924

Year of fee payment: 14

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: NL

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20080401

NLV4 Nl: lapsed or anulled due to non-payment of the annual fee

Effective date: 20080401

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20080917

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20080929

Year of fee payment: 16

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20081031

Year of fee payment: 16

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20090921

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20100531

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: FR

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090930

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20100401

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20090921